JPH09277996A - Extension structure for space structural body - Google Patents

Abstract

PROBLEM TO BE SOLVED: To extend a space structural body only by a simple structure without requiring a special power source for contributing to the lightening of a spacecraft in weight. SOLUTION: An extension structure 1 for extending a space structural body such as an antenna or solar battery paddle is provided with an extension part 10 capable of expansion and contraction which is fixed to a spacecraft on one end side, and which has an abutting plate 11 to be applied to the space structural body as a subject of extension on the other end side, an outer shell 20 capable of expansion and contraction which covers an outer circumference of the extension part 10, and of which surface is coated with UV-setting resin, and a containing part 40 having a cover 41 which can be opened/closed to contain the extension part 10 and the outer shell 20. The extension part 10 is composed of a shape memory metal of a spiral form, so that it is contracted to be contained inside the spacecraft at the time of launching of the spacecraft, and that it is transformed to be elongated by heat of sunlight in space after launching of the spacecraft.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an extension structure for extending a space structure in a spacecraft such as an artificial satellite, and more particularly, to an extension structure using only a simple structure without requiring a special power source. The present invention relates to an extension structure of a space structure capable of improving the productivity and reliability of the extension structure, and contributing to weight reduction of the spacecraft.

[0002]

2. Description of the Related Art In general, in a spacecraft such as an artificial satellite,
In order to deploy the antenna in outer space and extend the solar battery paddle, various extension structures are employed.
Here, as a conventional extension structure of a space structure, for example, there is one shown in FIG. 4 or FIG.

FIG. 4 is a schematic front view showing an extension structure of a conventional space structure, in which (a) shows a state of being accommodated in a spacecraft, and (b) shows a state of extension in space. Each is shown. In the conventional extension structure of a space structure in FIG. 4, one end (lower end in FIG. 4) is fixed to the spacecraft 203, and the other end is a space structure 204 to be extended (for example, an antenna). The configuration includes a coil spring 201 made of a shape memory metal fixed to a (sub-reflector) and a heater 202 for heating the coil spring 201.

The coil spring 201 is in an extended state (FIG. 4).
(State shown in (b)) is made of a shape memory alloy whose shape is memorized, and is shrunk to a size that can be stored in the spacecraft 203 by applying deformation at a low temperature (normal temperature on the ground). Reference numeral 205 denotes a telescopic supporting portion that supports the space structure 204 to be extended.

According to the extended structure of a space structure having such a configuration, before launching of the spacecraft, the coil spring 201 is stored in the contracted state at room temperature on the ground and the coil spring 201 is contracted. Space structure 204 and support 2
05 is also stored in the spacecraft. After the launch of the spacecraft, the heater 2 is activated by a command from the ground.
02 is heated to transform the coil spring 201 so that the coil spring 201 becomes an extension power and
Are extended, so that the space structure 204 can be extended.

On the other hand, FIG. 5 is a schematic perspective view showing an extension structure of another conventional space structure, and shows a state at the time of extension in space. The conventional extension structure shown in FIG. 5 includes a mandrel 301, a main slide hinge 302 and a synchronous slide hinge 30 movably engaged with the mandrel 301.
3 and both slide hinges 30 wound around the mandrel 301
2 and a spring 304 interposed therebetween. Then, both slide hinges 302, 3
At 03, deployment ribs 305, 306 are rotatably attached, and the distal ends of the ribs 305, 306 are attached to a space structure to be extended such as an antenna reflector (not shown).

According to the extension structure of such a space structure, first, before launching, the two slide hinges 3 are used.
02 and 303 are mechanically restrained by a fixing wire or the like while the spring 304 is compressed. And
In the outer space, the wire is cut using a pyrotechnic such as a wire cutter to release the restraint of the slide hinges 302 and 303, so that the synchronous slide hinge 303 extends upward by the elastic force of the spring 304, and The structure is to be deployed.

A conventional technique using such an extended structure of a space structure is disclosed in, for example, Japanese Patent Application Laid-Open No. 3-143003.
Truss antenna described in Japanese Patent Publication No.
For example, there is a mechanism for holding and releasing a deployed structure described in US Pat.

[0009]

However, in such a conventional extension structure of a space structure, the extension portion serving as a power source for the extension is provided with a heater for transforming the shape memory metal or a pyrotechnic such as a wire cutter. Need goods,
These facilities and electric power for driving them were required. For this reason, it is necessary to load these necessary equipment and devices on the spacecraft. As a result, the spacecraft becomes heavier, which contradicts the demand for weight reduction of spacecrafts such as artificial satellites. there were.

[0010] In addition, in such a conventional extension structure, an extension guide and a stopper for stopping the extension after extension and a structure and means for controlling the extension are separately required. These became heavy objects, and the spacecraft also became heavy.

The present invention has been proposed in order to solve such problems of the prior art, and can be extended only by a simple structure without requiring a special power source. An object of the present invention is to provide an extension structure of a space structure that can improve the productivity and reliability of the structure and can contribute to the weight reduction of the spacecraft.

[0012]

According to the first aspect of the present invention, there is provided a space structure extending structure for extending a space structure such as an antenna and a solar cell paddle in a spacecraft. An extension structure, one end of which is fixed to the spacecraft, and the other end of which includes a telescopically extendable portion that abuts on the space structure to be extended, and the extension portion launches the spacecraft. Sometimes, it is made of a spiral-shaped shape memory metal that contracts into a state that can be stored in the spacecraft, and after the spacecraft is launched, transforms and expands due to the heat of sunlight in space.

Further, in the extension structure of a space structure according to claim 2, the outer periphery of the extension portion is covered with an outer shell that expands and contracts in accordance with the expansion and contraction of the extension portion, and the surface of the outer shell is
It is configured to be coated with an ultraviolet curable resin.

Further, in the extension structure for a space structure according to claim 3, the outer periphery of the extension portion is covered with an outer shell that expands and contracts in accordance with the expansion and contraction of the extension portion, and an ultraviolet curable resin is coated on the outer shell. It has a configuration of impregnation.

According to the extension structure of the space structure of the present invention having such a configuration, the extension portion is formed of a spiral shape memory metal, and is transformed and extended by heating it with sunlight. Therefore, no special power source, device, structure, and the like for extending the extension section are required.

Further, by covering the extension portion with an outer shell coated or impregnated with an ultraviolet curable resin, the outer shell is sequentially hardened by ultraviolet rays of sunlight from the front end portion as the extension portion extends, and the extension portion is extended. Can hold and fix the shape of
There is no need to provide a structure or means for fixing the extended portion after extension.

As a result, in the extension structure of a space structure according to the present invention, a heater for starting the extension and a means for releasing the restraint, a structure for maintaining the shape after the extension, and the like, which are conventionally required, are not required at all. The space structure can be extended only by the structure, the spacecraft can be reduced in weight, and the productivity and reliability of the extended structure can be improved.

[0018]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of the extension structure of a space structure according to the present invention will be described below with reference to the drawings.
FIG. 1 is a perspective view showing a state when the extension structure of the space structure according to the present embodiment is stored, and FIG. 2 is a perspective view showing a state when the extension is also extended. FIG. 3 is a sectional view of a main part of the extension structure shown in FIGS.

In these figures, reference numeral 1 denotes an extension structure of a space structure in the present embodiment, which serves as an extension means for extending a space structure such as an antenna and a solar cell paddle in a spacecraft (not shown). . Reference numeral 10 denotes a telescopically extending portion, one end of which is fixed to the spacecraft, and the other end of which can contact a space structure to be extended.

As shown in FIGS. 1 and 2, the extension portion 10 is formed of a shape memory metal formed entirely in a spiral shape, and has the other end, that is, the tip end in the extension direction. A contact plate 11 is provided for contacting the space structure to be extended. The shape memory metal constituting the extension portion 10 stores the shape memory in the extended state (the state shown in FIG. 2), and is deformable at a low temperature (normal temperature on the ground) so that it can be stored in the spacecraft. It transforms and recovers due to the heat of sunlight in outer space.

As a result, when the spacecraft is launched, the extension unit 10 contracts so that it can be stored in the spacecraft (the state shown in FIG. 1), and after the spacecraft is launched, the sun expands in space. Transformation, restoration, and elongation are caused by the heat of light (the state shown in FIG. 2), and the space structure is pressed and extended by the contact plate 11.

Reference numeral 20 denotes an outer shell, which is a tubular layer material that covers the entire outer periphery of the extension portion 10 and is integrally attached to the extension portion 10 and the contact plate 11. To expand and contract. In the present embodiment, the outer shell 20 is formed of a film material or a cloth material in which various fibers are knitted so as to be able to expand and contract.

As shown in FIG. 3, the outer shell 20 is coated or impregnated with an ultraviolet curing resin 30 on its surface. That is, when the outer shell 20 is formed of a film material, the surface of the film material is coated with the ultraviolet curable resin 3.
0 is coated, and when the outer shell 20 is formed of a cloth material, the cloth material is impregnated with the ultraviolet curable resin 30. Thereby, the ultraviolet curing resin 30 of the outer shell 20 is cured by the ultraviolet rays of sunlight in the outer space, so that the shape of the extension portion 10 after extension can be maintained.

Numeral 40 denotes a storage portion, which protrudes from a side surface of a spacecraft (not shown) or the like so that the extension portion 10 in a contracted state can be stored. Reference numeral 41 denotes a cover of the storage unit 40, which can be automatically opened and closed by command control on the ground. In the case where the extension unit 10 can be directly stored in the spacecraft, the storage unit 40 can be omitted.

Next, the operation of the extended structure of the space structure according to the present embodiment having such a configuration will be described. First, before the launch of the spacecraft, the extension unit 10 is stored in the storage unit 40 in a contracted state at room temperature on the ground (the state shown in FIG. 1), and the space structure is also folded. Can be stored in the spacecraft. At this time, the cover 41 of the storage section 40 is in a closed state. Thus, when the spacecraft is launched, the extension structure 1 and the space structure do not hinder the launch.

Next, after the launch of the satellite, the extension structure 1 is extended in space. That is, first, the cover 41 of the storage unit 40 is opened by a command from the ground, and the attitude of the spacecraft is controlled so that the extension structure 1 is directed to the direction of irradiating sunlight. When the extension structure 1 is directed to sunlight, the extension part 10 is heated by the heat of sunlight, and the shape memory alloy forming the extension part 10 is transformed and restored. Thereby, the extension unit 10 extends.

At the same time as the extension unit 10 extends,
Since the outer shell 20 covering the outer periphery of the extension portion 10 is also irradiated with sunlight, the ultraviolet curable resin 30 on the surface of the outer shell 20 starts curing by the ultraviolet rays of the sunlight sequentially from the front end side in the extension direction, and extends. The shape of the part 10 is held and fixed. As a result, the extension of the extension portion 10 serves as extension power to bring the contact plate 11 into contact with a space structure (not shown) to press and extend the space structure, and the outer shell 20 is hardened.
The extension unit 10 itself serves as a support member for supporting the space structure.

As described above, according to the extension structure of the space structure of the present embodiment, the extension portion 10 is formed of a spiral shape memory metal, and is transformed and extended by heating it with sunlight. Therefore, no special power source, device, structure or the like for extending the extension unit 10 is required. That is, since a heat supply device such as a heater for transforming the shape memory metal is not required, the number of components is significantly reduced as compared with the conventional one.

Further, the extending portion 10 is made of an ultraviolet curable resin 30.
By covering or impregnating the outer shell 20,
In accordance with the extension of the extension portion 10, the outer shell 20 is sequentially cured by ultraviolet rays of sunlight from the tip portion, and the shape of the extension portion 10 can be maintained and fixed, so that the extension portion 10 after extension is fixed. There is no need to provide a structure or means such as a cylinder or a stopper.

As a result, there is no need for a heater for starting expansion or a means for releasing restraint, which is required in the conventional structure for extending a space structure, or a structure for maintaining the shape of the space structure after extension. The space structure can be extended, the weight of the spacecraft can be reduced, and the productivity and reliability of the extended structure can be improved.

[0031]

As described above, according to the extension structure of the space structure of the present invention, it is possible to extend only by a simple structure without requiring a special power source, and the productivity of the extension structure can be improved. The reliability can be improved and the weight of the spacecraft can be reduced.

[Brief description of drawings]

FIG. 1 is a perspective view showing a state where an extended structure of a space structure according to an embodiment of the present invention is stored.

FIG. 2 is a perspective view showing a state at the time of extension of the extension structure of the space structure according to the embodiment of the present invention.

FIG. 3 is a sectional view of an essential part of the extension structure of the space structure shown in FIGS. 1 and 2.

FIG. 4 is a schematic front view showing an extension structure of a conventional space structure, and FIG.
(B) shows the state at the time of extension in outer space.

FIG. 5 is a schematic perspective view showing an extension structure of another conventional space structure, showing a state at the time of extension in outer space.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 ... Extension structure 10 ... Extension part 11 ... Contact plate 20 ... Outer shell 30 ... Ultraviolet curing resin 40 ... Storage part 41 ... Cover

Claims (3)

[Claims] 1. An extension structure for extending a space structure such as an antenna and a solar cell paddle in a spacecraft, wherein one end of the spacecraft is fixed to the spacecraft, and the other end of the spacecraft to be extended. The spacecraft has a telescopically extending portion that abuts on a structure, and when the spacecraft is launched, it contracts to a state that can be stored in the spacecraft. An extension structure for a space structure, comprising a spiral shape memory metal that is transformed by heat of sunlight in space and extends. 2. The space structure according to claim 1, wherein the outer periphery of the extension portion is covered with an outer shell that expands and contracts in accordance with the expansion and contraction of the extension portion, and the surface of the outer shell is coated with an ultraviolet curable resin. Extension structure. 3. The extension of the space structure according to claim 1, wherein the outer periphery of the extension portion is covered with an outer shell that expands and contracts in accordance with the expansion and contraction of the extension portion, and the outer shell is impregnated with an ultraviolet curable resin. Construction.